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WO2008098743A1 - Alliage d'al-mg pour plaques de blindage - Google Patents

Alliage d'al-mg pour plaques de blindage Download PDF

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Publication number
WO2008098743A1
WO2008098743A1 PCT/EP2008/001070 EP2008001070W WO2008098743A1 WO 2008098743 A1 WO2008098743 A1 WO 2008098743A1 EP 2008001070 W EP2008001070 W EP 2008001070W WO 2008098743 A1 WO2008098743 A1 WO 2008098743A1
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WO
WIPO (PCT)
Prior art keywords
alloy plate
aluminum alloy
plate according
range
cold working
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/EP2008/001070
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English (en)
Inventor
Ingo Günther KRÖPFL
Claus Jürgen MORITZ
Stefan Moldenhauer
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Novelis Koblenz GmbH
Original Assignee
Aleris Aluminum Koblenz GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Aleris Aluminum Koblenz GmbH filed Critical Aleris Aluminum Koblenz GmbH
Priority to CN200880004376A priority Critical patent/CN101631882A/zh
Priority to KR1020097016058A priority patent/KR20090109549A/ko
Priority to EP08707685.7A priority patent/EP2118327B9/fr
Priority to AU2008214846A priority patent/AU2008214846B2/en
Publication of WO2008098743A1 publication Critical patent/WO2008098743A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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Classifications

    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • C22F1/047—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon of alloys with magnesium as the next major constituent
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
    • B22D21/00—Casting non-ferrous metals or metallic compounds so far as their metallurgical properties are of importance for the casting procedure; Selection of compositions therefor
    • B22D21/002—Castings of light metals
    • B22D21/007—Castings of light metals with low melting point, e.g. Al 659 degrees C, Mg 650 degrees C
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C1/00—Making non-ferrous alloys
    • C22C1/06—Making non-ferrous alloys with the use of special agents for refining or deoxidising
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22C—ALLOYS
    • C22C21/00—Alloys based on aluminium
    • C22C21/06—Alloys based on aluminium with magnesium as the next major constituent
    • C22C21/08—Alloys based on aluminium with magnesium as the next major constituent with silicon
    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/04—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of aluminium or alloys based thereon
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41H—ARMOUR; ARMOURED TURRETS; ARMOURED OR ARMED VEHICLES; MEANS OF ATTACK OR DEFENCE, e.g. CAMOUFLAGE, IN GENERAL
    • F41H5/00—Armour; Armour plates
    • F41H5/02—Plate construction
    • F41H5/023—Armour plate, or auxiliary armour plate mounted at a distance of the main armour plate, having cavities at its outer impact surface, or holes, for deflecting the projectile

Definitions

  • This invention pertains to an aluminium alloy plate product having a gauge of 10 mm or more. More particularly, this invention pertains to AIMg alloys that are suitable for armour plate, yet have improved performance properties, particularly improved resistance against incoming kinetic energy projectiles in combination with an improved formability.
  • alloy designations and temper designations refer to the Aluminum Association designations in Aluminum Standards and Data and the Registration Records, as published by the Aluminum Association.
  • aluminium alloys Because of their light weight, aluminium alloys have found wide use in military applications, including military vehicles such as personnel carriers. The light weight of aluminium allows for improved performance and ease of transporting equipment, including air transport of military vehicles. In some vehicles it is advisable to provide shielding or protection against assault, by providing armour plate to protect the occupants of the vehicle. Aluminum has enjoyed substantial use as armour plate, and there are a number of armour plate specifications for the use of different aluminium alloys.
  • aluminium alloy armour plate The most relevant requirements for aluminium alloy armour plate are resistance to projectiles, good corrosion resistance, and in some applications, good weldability. Ballistic tests are often conducted with armour piercing ("AP") projectiles such as the 7.62 mm AP M2 and with fragment simulating projectiles ("FSP") such as the common 20 mm projectile.
  • AP armour piercing
  • FSP fragment simulating projectiles
  • Aluminum alloys which satisfy all the requirements for armour plate are desirable, and these desires have been met to varying degrees.
  • Aluminum alloys AA5083 and AA5456 are covered in the U.S. Military Specification for armour plate MIL-DTL-46027J (September 1998), and the alloy AA7039 is covered in the U.S. Military Specification MIL-DTL-46063H (September 1998).
  • the alloy AA7039 armour plate is better than AA5083 and AA5456 armour plate, although the advantage is more for armour piercing ballistic performance and less so for fragment simulation performance, at least according to the military specifications.
  • the alloy AA7039 can present corrosion or stress corrosion problems to a much greater degree than AA5083 and AA5456.
  • the alloy AA7039 is very difficult to weld.
  • the AA7039 alloy when used for armour plate applications is commonly in a T6 temper and the AA5083 and AA5456 alloys when used for armour plate applications is used in the H 131 temper.
  • compositional ranges for AA5083 are, in weight percent: Mg 4.0 to 4.9, Mn 0.40 to 1.0, Cr 0.05 to 0.25, Si max. 0.40, Fe max. 0.40, Cu max. 0.10, Zn max. 0.25, Ti max. 0.15, impurities each element ⁇ 0.05, total ⁇ 0.15, balance aluminium.
  • the nominal composition for the AA5083 alloy is about 4.4 wt.% Mg, 0.7 wt.% Mn and 0.15 wt.% Cr.
  • compositional ranges for AA5456 are, in weight percent: Mg 4.7 to 5.5, Mn 0.50 to 1.0, Cr 0.05 to 0.20, Si max. 0.25, Fe max. 0.40, Cu max. 0.10, Zn max. 0.25, Ti max. 0.20, impurities each element ⁇ 0.05, total ⁇ 0.15, balance aluminium.
  • the nominal composition for the AA5456 alloy is about 5.0 wt.% Mg, 0.7 wt.% Mn and 0.15 wt.% Cr.
  • compositional ranges for AA7039 are, in weight percent: Zn 3.5 to 4.5, Mg 2.3 to 3.3, Mn 0.10 to 0.40, Cr 0.15 to 0.25, Si max. 0.30, Fe max. 0.40, Cu max. 0.10, Ti max. 0.10, impurities each element ⁇ 0.05, total ⁇ 0.15, balance aluminium.
  • the nominal composition for the AA7039 alloy is about 4 wt.% Zn, 2.8 wt.% Mg, 0.25 wt.% Mn and 0.20 wt.% Cr.
  • composition percents in the present specification are weight percents.
  • aluminium alloy armour plate The most important requirements for aluminium alloy armour plate are resistance to projectiles, good corrosion resistance and stress corrosion resistance in particular, and in modern applications, good weldability. Ballistic tests are often conducted with armour-piercing projectiles such as 0.30 inch calibre projectiles and with fragment-simulating projectiles such as the common 20 mm projectile. Aluminum alloys which satisfy all the requirements for armour plate are desirable.
  • AA5059 alloy registered with the Aluminum Association in June 1999.
  • the registered compositional ranges for AA5059 are, in wt.%: Mg 5.0 to 6.0, Mn 0.6 to 1.2, Zn 0.40 to 0.9, Zr 0.05 to 0.25, Cr max. 0.25, Si max. 0.45, Fe max. 0.50, Cu max. 0.25, Ti max.0.20, impurities each element ⁇ 0.05, total ⁇ 0.15, balance aluminium.
  • This aluminium alloy is also disclosed in US-6,238,495-B2 and US-6,342,113-B2, both incorporated herein by reference in their entireties.
  • the aluminium alloy is for the construction of large welded structures such as storage containers and vessels for marine and land transportation.
  • the alloy has found in particular commercial usage in shipbuilding application, whereby the aluminium alloy is typically in the H321 -temper or O-temper and has a thickness or gauge of less than 20 mm.
  • the H321 temper was reached by a cold rolling reduction of 40% followed by heat treating by soaking the cold rolled product at 25O 0 C for one hour.
  • the O-temper was reached by a cold rolling reduction of 40% followed by soaking to cold rolled product at 525 0 C for a period of 15 minutes.
  • An object of the present invention is to provide an improved 5000 series alloy that has very good weldablility, yet exhibits good corrosion performance and high resistance to incoming kinetic energy projectiles.
  • a further object is to provide a 5000 series alloy product having at least similar ballistic properties as its AA5083-H131 counterpart but with a higher elongation at fracture.
  • an aluminium alloy plate having improved resistance against incoming kinetic energy projectiles, the plate having a gauge of 10 mm or more and the aluminium alloy having a chemical composition comprising, in weight percent:
  • Mg about 4.0 to 6.0, preferably about 4.3 to 5.7
  • Mn about 0.2 to 1.4, preferably about 0.4 to 1.2
  • Zn max. 0.9 preferably about 0.20 to 0.90, preferably about 0.35 to 0.70
  • the alloy plate is obtained by a manufacturing process comprising casting, preheating and/or homogenisation, hot rolling, a first cold working operation, an annealing treatment at a temperature of less than 35O 0 C, followed by a second cold working operation.
  • the plate has an at least 4% improvement, and preferably an at least 5% improvement, in the V50 limit compared to an AA5083-H131 counterpart, as measured by the 30 AMP2 test according to MIL-DTL-46027J of September 1998.
  • an AA5083-H131 counterpart it is meant an aluminium alloy plate having a composition as defined above for AA5083, and processed and heat treated to H131 temper and having the same dimensions of length, width and thickness as the plate of the present invention to which it is compared.
  • a typical counterpart has a composition within the elemental window of about 4.4 wt.% Mg, 0.7 wt.% Mn, 0.15 wt.% Cr, 0.40 wt.% Si max., 0.40 wt.% Fe max., 0.10 wt.% Cu max., 0.25 wt.% Zn max., 0.15 wt.% Ti max., impurities each element ⁇ 0.05 wt.%, total ⁇ 0.15 wt.%, and balance aluminium.
  • a typical processing route for obtaining an H131 temper is by means of casting an ingot of defined composition, homogenisation and/or preheat prior to hot rolling, hot rolling to intermediate gauge, cold rolling to final gauge using a cold rolling deformation of about 15 to 25%, followed by a stretching operation of maximum 1.5% to achieve flatness and straightness requirements. No annealing is carried out subsequently to any of the cold rolling or stretching steps.
  • a plate within the elemental composition and processed as described for the present invention having the at least 4% improvement in the V50 limit over a single AA5083-H131 counterpart meets the feature of being a plate having an at least 4% improvement in the V50 limit compared to an AA5083-H131 counterpart.
  • a plate within the elemental composition described for the present invention having the at least 4% improvement in the V50 limit over an AA5083-H131 counterpart having a composition of 4.4 wt.% Mg, 0.7 wt.% Mn, 0.15 wt.% Cr, 0.2 wt.% Si, 0.2 wt.% Fe, 0.05 wt.% Cu, 0.15 wt.% Zn, 0.1 wt.% Ti, impurities each element ⁇ 0.05 wt.%, total ⁇ 0.15 wt.%, and balance aluminium, meets the feature of being a plate having an at least 4% improvement in the V50 limit compared to an AA5083-H131 counterpart.
  • an AA7039-T6 counterpart is an aluminium alloy plate having a composition as defined above for AA7039 and processed and heat treated to a T6 temper and having the same dimensions of length, width and thickness as the plate of the present invention to which it is compared.
  • a typical counterpart has a composition within the elemental window of about 4 wt.% Zn, 2.8 wt.% Mg, 0.25 wt.% Mn and 0.20 wt.% Cr, 0.30 wt.% Si max., 0.40 wt.% Fe max., 0.10 wt.% Cu max., 0.10 wt.% Ti max., impurities each element ⁇ 0.05 wt.%, total ⁇ 0.15 wt.%, balance aluminium; for example, 4 wt.% Zn, 2.8 wt.% Mg, 0.25 wt.% Mn and 0.20 wt.% Cr, 0.20 wt.% Si, 0.20 wt.% Fe 1 0.05 wt.% Cu, 0.05 wt.% Ti, impurities each element ⁇ 0.05 wt.%, total ⁇ 0.15 wt.%, balance aluminium.
  • the armour plate is useful, for example, in military and/or anti-terrorist applications to protect authorized law enforcement and/or military personnel. For example, authorized law enforcement and/or military personnel patrolling areas containing known or suspected terrorists could do so while in vehicles armoured with the present armour plate.
  • Fig. 1 shows an up-armoured Multipurpose Wheeled Vehicle, or "HMMWV”.
  • Fig. 2 shows a Stryker vehicle.
  • Fig. 3 shows a Bradley M2/M3 vehicle. DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS
  • the present invention provides an aluminium alloy plate having improved resistance against incoming kinetic energy projectiles, the plate having a gauge of 10 mm or more and the aluminium alloy having a chemical composition comprising, in weight percent:
  • Mg about 4.0 to 6.0, preferably about 4.3 to 5.7, for example 4.9 to 5.6 Mn about 0.2 to 1.4, preferably about 0.4 to 1.2, for example 0.65 to 0.9
  • Zn about 0.9 max., preferably about 0.20 to 0.90, preferably about 0.35 to 0.70, for example 0.45 to 0.6
  • Zr ⁇ 0.3 preferably about 0.05 to 0.25, for example about 0.05 to 0.15 Cr ⁇ 0.3, for example about 0.08 to 0.15
  • Sc ⁇ 0.5 for example about 0.08 to 0.45, 0.2 to 0.45, or ⁇ 0.1 , but preferably 0.05 to 0.30, 0.05 to 0.20, or 0.05 to 0.15
  • Fe ⁇ 0.5 preferably ⁇ 0.25, for example ⁇ 0.14
  • Si ⁇ 0.45 preferably ⁇ 0.2, for example ⁇ 0.14 Ag ⁇ 0.4, for example ⁇ 0.01
  • the alloy plate is obtained by a manufacturing process comprising casting, preheating and/or homogenisation, hot rolling, a first cold working operation, an annealing treatment at a temperature of less than 35O 0 C, followed by a second cold working operation.
  • the plate has an at least 4%, and preferably an at least 5%, improvement in the V50 limit compared to an AA5083-H131 counterpart, as measured by the 30 AMP2 test according to MIL-DTL-46027J of September 1998. This improvement is particularly pronounced for the alloy plate products having 4.9% Mg of more.
  • the plate has an at least 4% improvement, and preferably an at least 6% improvement, in the V50 limit compared to an AA5083-H131 counterpart, as measured by the 20 mm FSP test according to MIL-DTL-46027J of September 1998. This improvement is particularly pronounced for the alloy plate products having 4.9% Mg of more.
  • the aluminium alloy plate according to the present invention offers a plate product ideally suitable for armour plate applications having at least similar ballistic properties, and in the best examples even significantly improved ballistic properties, compared to its AA5083-H131 counterpart in combination with improved formability expressed in elongation at fracture.
  • the aluminium alloy plate according to the present invention offers also a plate product having ballistic properties close to its AA7039-T6 counterpart, but in combination with very good weldability and improved corrosion resistance performance, in particular in stress corrosion resistance, compared to the AA7039-T6 alloy.
  • This combination of ballistic properties, very good weldability and corrosion resistance performance favours the alloy plate of the present invention for the application as armour plate.
  • An important advantage of the present invention is the improved Mass Efficiency compared to AA5083-H131 and even compared to AA7039-T6 counterparts.
  • the alloy product according to the invention has a lower specific density measured at 2O 0 C compared to both the AA5083 and AA7039 alloys resulting in a favourable strength-to-weight ratio or specific strength (tensile strength divided by specific density). This improvement is particularly pronounced for the alloy plate products having 4.9% Mg of more.
  • the Mass Efficiency is a measure for the FSP performance and relates also to the specific density and allows for a fair comparison of various armour plate materials of similar gauge against each other. Mass Efficiency or "E m " is being defined as the weight per unit area of a reference material, for example an AA 5083-H131 counterpart alloy, required for defeating a given ballistic threat divided by the weight per unit area of the subject material.
  • Mg content is limited to 6% because alloy products having a higher Mg content are not very easy to manufacture. Furthermore, a Mg content of more than 6% does not result in any significant strength increase, whereas the corrosion resistance, in particular the resistance against intergranular corrosion, exfoliation corrosion and stress corrosion, deteriorate very fast at higher Mg levels.
  • the Mg content should be more than 4.0% in order to provide amongst others a sufficient strength levels for the preferred applications of the alloy plate for armour plate applications. More preferably the Mg content is at least 4.3%, and more preferably at least 4.9%. If desired Mg + Mn is greater than 6.8% or Mg + Mn is less than 5.9%.
  • the plate product preferably has a Zn content in a range of about 0.2 to 0.9 wt.% to enhance weldability and the corrosion resistance of the base plate.
  • the plate product preferably has a Zr content in a range of about 0.05 to 0.25%, for example >0.16 to 0.25, to further improve the weldability and the corrosion resistance of the base plate.
  • Ti may be purposively added up to about 0.3%, for example >0.16 to 0.3, for grain-refiner purposes during casting and/or welding.
  • Cr and/or Ti may be absent.
  • a further improvement of the properties, particularly the corrosion resistance, of the aluminium alloy plate product according to the invention is obtained when both Ti and Cr are present in considerable amounts within the defined range.
  • Ti and Cr are present in considerable amounts within the defined range.
  • titanium and chromium are present in equal or about equal quantities in the aluminium alloy product, and wherein Cr is in a range of about 0.08 to 0.25% and Ti is a range of about 0.1 to 0.2%.
  • Zr in the previously defined range of 0.05 to 0.25% may be present in addition to the combined presence of Ti and Cr in the defined ranges.
  • Sc may purposively be added up to 0.5%, preferably in a range of 0.05 to 0.3%, and more preferably in the range of 0.05 to 0.15%, to further increase the resistance to incoming kinetic energy projectiles.
  • the aluminium alloy plate according to the present invention has a composition within the range of AA5059.
  • the alloy plate has a proof strength ("PS") of at least about 250 MPa 1 preferably at least about 255 MPa, and more preferably at least about 260 MPa, when measured in its L-direction.
  • PS proof strength
  • the alloy plate has a ultimate tensile strength ("UTS") of at least about 320 MPa, preferably at least about 330 MPa, and more preferably at least about 340 MPa, when measured in either in its L-direction or LT direction.
  • UTS ultimate tensile strength
  • the alloy plate has an elongation to fracture measured in a tensile test according to ASTM B557 in the L-direction of more than 10%, and preferably of more than 12%.
  • the elongation in the LT- direction is 13% or more, and in the best examples of 14% or more.
  • the plate according to this invention is ideally suitable as armour plate for application in armoured vehicles, in particular armoured military vehicles.
  • the gauge range or thickness range of the aluminium alloy plate is of more than about 10 mm.
  • a suitable upper-limit for aluminium alloy plate is about 100 mm.
  • a preferred gauge range is of about 15 to 75 mm, and more preferably in a range of about 25 to 75 mm.
  • the alloy plate at final gauge after the cold working operation is not subjected to of a further heat-treatment such that no substantial recovery occurs in the alloy plate.
  • a heat-treatment of for example 30 min at 8O 0 C can be carried out as this merely stabilises the alloy product.
  • a heat treatment of 30 min or 60 min at 25O 0 C to obtain an H321 temper results amongst others in an undesirable increase of the ductility.
  • Any high temperature heat- treatment after cold working to final thickness is preferably to be avoided.
  • the alloy described herein can be ingot derived and can be provided as an ingot or slab by casting techniques including those currently employed in the art.
  • a preferred practice is semi-continuous casting of large ingots, for instance 350 or 600 mm in thickness by about 1000 mm or more in width by about 3.5 m or more in length.
  • Such large ingots are preferred in practicing the invention especially in making large plate products for use in armour plate applications.
  • the aluminium alloy stock is preferably preheated or homogenized at a temperature of at least 48O 0 C prior to hot rolling in single or multiple steps.
  • the temperature should not be too high, and should typically not exceed 535 0 C.
  • the time at temperature for a large commercial ingot can be about 2 to 24 hours. A longer period, for example 48 hours or more, has no immediate adverse effect on the desired properties, but is economically unattractive.
  • the heating rate is typically in a range of 30 to 40°C/hour.
  • the alloy is hot rolled to reduce its thickness by at least about 30% of its initial (before any hot rolling) thickness, preferably by about 50% or more, for instance 60 or 65% or more of its thickness when using large commercial starting stock (for instance around 400 mm or more thick) using a reversing hot mill which rolls the metal back and forth to squeeze its thickness down.
  • the initial hot rolling can be done in increments using different rolling mills. It can also include conventional reheating procedures at around 500 0 C or so between the rolling passes to replace lost heat.
  • the alloy product is cold worked by means of a first cold working operation selected from the group consisting of (i) stretching in a range of 2 to 15%, and (ii) cold rolling with a cold roll reduction in a range of 4% to less than 45%.
  • a second cold working operation selected from the group consisting of (i) stretching in a range of about 2 to 15%, and (ii) cold rolling with a cold roll reduction in a range of about 4% to less than 25%.
  • the plate is subjected to an annealing treatment at a temperature of less than 35O 0 C appropriate to enhance workability, preferably at a temperature of 300 0 C or less, and more preferably in a temperature range of about 22O 0 C to 300°C.
  • the soaking temperature for the annealing treatment would typically be in the range of 10 minutes to 10 hours.
  • the cold stretching in the first and second cold working operation consists of a stretch in a range of about 4 to 15%, and preferably in a range of about 4 to 10%.
  • Stretching is defined as the permanent elongation in the direction of stretching, commonly in the L-direction of the plate product.
  • the stretching operation is preferably carried out when producing thicker gauge plate products, such as for plate products having a final gauge of 25 mm or more, and preferably of 38 mm or more. It has been found that a cold stretching operation allows for more uniform properties over the thickness of the plate compared to a cold rolling operation.
  • the cold working steps can also be carried out in combination, although in a less preferred mode, for example by carrying out a 10% cold rolling operation followed by an 8% stretching operation.
  • the aluminium alloy plate product according to the invention can be welded by means of all regular welding techniques such as MIG and friction stir welding. After the welding operation there is no need for further heat treatment to obtain maximum properties or to recover some of the losses in mechanical properties as a resultant of the heat input during the welding operation and therefore there are less costs in the production of armoured vehicles.
  • the aluminium plate can be welded using regular filler wires such as AA5183 or by modified filler wires having a higher Mg- and/or Mn- content.
  • a further aspect of the invention relates to a method of use of the aluminium alloy product as armour plate in an armoured vehicle, in particular in military vehicles such as Tracked Combat Systems, Armoured Personnel Carriers, Armoured Support Systems, Amphibious Assault Systems, Advanced Assault Amphibious Vehicles or Armed Robotic Vehicles.
  • military vehicles such as Tracked Combat Systems, Armoured Personnel Carriers, Armoured Support Systems, Amphibious Assault Systems, Advanced Assault Amphibious Vehicles or Armed Robotic Vehicles.
  • When applied in such armoured vehicles it will be a form of a welded configuration such that it forms integral armour.
  • Hang-on armour plate is possible for the aluminium alloy plate according to this invention, but is not the most preferred application.
  • Fig. 1 shows an up-armoured US Army High Mobility Multipurpose Wheeled Vehicle, or "HMMWV” 110.
  • Fig. 2 shows a Stryker vehicle 120.
  • Fig. 3 shows a Bradley M2/M3 vehicle 120.
  • These vehicles 110, 120, 130 can be modified in view of the present invention to have plates of the armour of the present invention applied, for example by welding, to an outer surface or other locations of the vehicle suitable for armour protection.
  • the armour is vital protection against small arms, rocket- propelled grenades, or RPGs, and "improvised explosive devices," or IEDs. Additional information on armoured vehicles is available at the website of Global Security.org, Alexandria, VA, http://www.globalsecurity.org/military/systems/ground/hmmwvua.htm, July 2006.
  • the ingots have been scalped, then preheated for 8 hours at 51O 0 C, then hot rolled to a gauge of 28 to 57 mm, and then cold stretched for 6% as a first cold working operation, then annealed with about 15 minutes soak at about 250°C, and then cold stretched about 6% or subjected to a cold rolling reduction of about 7% as a second cold working operation resulting in the final plate thickness.
  • the hot rolling practice was such that the cold working reduction could be varied to investigate the mechanical properties as function of the final plate thickness.
  • the cold worked plates received no further heat- treatment after the last cold working operation.
  • the mechanical properties have been measured according to ASTM B557 in the LT direction and the L-direction.
  • the mechanical properties are listed in Table 1.
  • the mechanical property levels of the alloy product when manufactured according to this invention has a combination of significantly higher properties and elongation compared to an AA5083-H131 counterpart.
  • Typical elongation for the AA5085-H131 of similar thickness are about 9% in the L-direction together a Proof Strength of 255 MPa and an Ultimate Tensile Strength of 310 MPa, and about 9.5% in the LT-direction and a Proof strength of 256 MPa and an Ultimate Tensile Strength of 311 MPa.
  • This example relates to aluminium alloy plate of 38.8 mm gauge according to this invention, in particular the preferred embodiment of the AA5059 alloy manufactured according to the process and chemical composition of Example 1.
  • the plate was tested for its ballistic properties and compared against its armour plate counterpart AA5083-H 131.

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Abstract

L'invention porte sur une plaque d'alliage d'aluminium d'un calibre de 10 mm ou plus et présentant une résistance améliorée aux projectiles à forte énergie cinétique. Ledit alliage comprend en % en poids: Mg 4,0 à 6,0, Mn 0,2 à 1,4, Zn 0,9 maximum, Zr < 0,3, Cr < 0,3, Sc < 0,5, Ti < 0,3, Fe < 0,5, Si < 0,45, Ag < 0,4, Cu < 0,25, plus d'autres éléments et les impuretés inévitables à raison de < 0,05, le total < 0,20 du reliquat d'aluminium. Le procédé de fabrication comprend les opérations suivantes: coulée; préchauffage et/ou homogénéisation; laminage à chaud; premier travail à froid; recuit à moins de 350°C, et deuxième travail à froid.
PCT/EP2008/001070 2007-02-12 2008-02-12 Alliage d'al-mg pour plaques de blindage Ceased WO2008098743A1 (fr)

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CN200880004376A CN101631882A (zh) 2007-02-12 2008-02-12 适合装甲板应用的Al-Mg合金产品
KR1020097016058A KR20090109549A (ko) 2007-02-12 2008-02-12 장갑판재용 Ａｌ-Ｍｇ 합금
EP08707685.7A EP2118327B9 (fr) 2007-02-12 2008-02-12 Alliage d'al-mg pour plaques de blindage
AU2008214846A AU2008214846B2 (en) 2007-02-12 2008-02-12 Al-Mg alloy product suitable for armour plate applications

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WO2014114625A1 (fr) * 2013-01-25 2014-07-31 Aleris Rolled Products Germany Gmbh Procédé de formation d'un produit plat en alliage al-mg
CN101863307B (zh) * 2009-04-15 2016-12-14 阿勒里斯铝业科布伦茨有限公司 用于飞机机身的蒙皮板
WO2018104004A1 (fr) * 2016-12-08 2018-06-14 Aleris Rolled Products Germany Gmbh Procédé de fabrication d'un produit de plaque d'alliage d'aluminium résistant à l'usure
US20210269906A1 (en) * 2018-06-11 2021-09-02 Aleris Rolled Products Germany Gmbh Method of manufacturing an al-mg-mn alloy plate product having an improved corrosion resistance
US11352686B2 (en) 2015-06-25 2022-06-07 Hydro Aluminium Rolled Products Gmbh High-strength and easily formable AlMg-strip, and method for producing the same
WO2022240538A2 (fr) 2021-04-14 2022-11-17 Constellium Rolled Products Ravenswood, Llc Produit laminé en alliage d'al-mg épais convenant à des applications pour plaque de protection balistique

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KR101073368B1 (ko) * 2009-03-19 2011-10-13 한국기계연구원 알루미늄 합금 판재의 제조방법
CN101863307A (zh) * 2009-04-15 2010-10-20 阿勒里斯铝业科布伦茨有限公司 用于飞机机身的蒙皮板
CN101863307B (zh) * 2009-04-15 2016-12-14 阿勒里斯铝业科布伦茨有限公司 用于飞机机身的蒙皮板
US9217622B2 (en) * 2009-07-24 2015-12-22 Alcoa Inc. 5XXX aluminum alloys and wrought aluminum alloy products made therefrom
US20110017055A1 (en) * 2009-07-24 2011-01-27 Alcoa Inc. 5xxx aluminum alloys and wrought aluminum alloy products made therefrom
EP2456899A2 (fr) 2009-07-24 2012-05-30 Alcoa Inc. Alliages en aluminium 5xxx améliorés et produits en alliage d'aluminium corroyé élaborés à partir de ces alliages
RU2465365C1 (ru) * 2011-05-31 2012-10-27 Федеральное государственное автономное образовательное учреждение высшего профессионального образования "Белгородский государственный национальный исследовательский университет" Способ получения сверхпластичных заготовок из алюминиевых сплавов на основе системы алюминий-магний-скандий
RU2483136C1 (ru) * 2011-12-30 2013-05-27 Закрытое акционерное общество "Алкоа Металлург Рус" Способ изготовления катаных изделий из деформируемых термически неупрочняемых сплавов системы алюминий - магний
WO2014114625A1 (fr) * 2013-01-25 2014-07-31 Aleris Rolled Products Germany Gmbh Procédé de formation d'un produit plat en alliage al-mg
EP2948571B1 (fr) 2013-01-25 2018-09-12 Aleris Rolled Products Germany GmbH Procédé de fabrication d'un produit de feuille d'alliage ai-mg
US10335841B2 (en) 2013-01-25 2019-07-02 Aleris Rolled Products Germany Gmbh Method of forming an Al—Mg alloy plate product
US11352686B2 (en) 2015-06-25 2022-06-07 Hydro Aluminium Rolled Products Gmbh High-strength and easily formable AlMg-strip, and method for producing the same
WO2018104004A1 (fr) * 2016-12-08 2018-06-14 Aleris Rolled Products Germany Gmbh Procédé de fabrication d'un produit de plaque d'alliage d'aluminium résistant à l'usure
US11193193B2 (en) 2016-12-08 2021-12-07 Aleris Rolled Products Germany Gmbh Method of manufacturing a wear-resistant aluminium alloy plate product
US20210269906A1 (en) * 2018-06-11 2021-09-02 Aleris Rolled Products Germany Gmbh Method of manufacturing an al-mg-mn alloy plate product having an improved corrosion resistance
US12091735B2 (en) * 2018-06-11 2024-09-17 Novelis Koblenz Gmbh Method of manufacturing an Al—Mg—Mn alloy plate product having an improved corrosion resistance
WO2022240538A2 (fr) 2021-04-14 2022-11-17 Constellium Rolled Products Ravenswood, Llc Produit laminé en alliage d'al-mg épais convenant à des applications pour plaque de protection balistique
WO2022240538A3 (fr) * 2021-04-14 2023-02-16 Constellium Rolled Products Ravenswood, Llc Produit laminé en alliage d'al-mg épais convenant à des applications pour plaque de protection balistique
US12480192B2 (en) 2021-04-14 2025-11-25 Constellium Rolled Products Ravenswood, Llc Thick Al—Mg alloy rolled product suitable for armor plate applications

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EP2118327A1 (fr) 2009-11-18
AU2008214846B2 (en) 2012-05-24
EP2118327B9 (fr) 2018-02-28
EP2118327B1 (fr) 2017-07-12
AU2008214846A1 (en) 2008-08-21
KR20090109549A (ko) 2009-10-20
US9255315B2 (en) 2016-02-09
US20150284831A1 (en) 2015-10-08
RU2461638C2 (ru) 2012-09-20
CN101631882A (zh) 2010-01-20
RU2009130603A (ru) 2011-02-20

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